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LUVOIR Engineering Team Update
27 November 2018
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Agenda
• Study Schedule
• Architecture Status• LUVOIR-A
• LUVOIR-B
• Update on Study Deliverables
• Issues
27 November 2018 2STDT Face-to-Face Meeting
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Study Schedule
27 November 2018 3
Deliverable Due Date Completed Completed On
M1Comments on Study Requirements and
Deliverables4/29/2016
O1 Initial Technology Gap Assessment 6/30/2016
O2 Update Technology Gap Assessments 6/30/2017
M4 Interim Report to NASA HQ 3/30/2018 3/26/2018
O3 Update Technology Gap Assessments 6/30/2018No longer required as of
4/19/2018
M6Draft Final Report due to Large Mission Concept
Independent Assessment Team (LCIT*)2/28/2019
M6’ First meeting of LCIT with STDT’s 3/2019
M6’’ Second meeting of LCIT with STDT’s 5/2019
M6’’’ LCIT final report to NASA HQ 6/2019
M7 STDT Final Report due to NASA HQ 6/2019
M8 HQ Submits final report to Decadal 7/2019
*LCIT process, charter, and schedule is still tentative and may change.STDT Face-to-Face Meeting
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The LUVOIR Architectures
27 November 2018 STDT Face-to-Face Meeting 4
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 5
LUVOIRMission
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 6
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Mission
Segment
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 7
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Payload
Element
Spacecraft
Element
Mission
Segment
Element
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 8
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Payload
Element
Spacecraft
Element
Optical
Telescope
Assembly
(OTA)
Extreme
Coronagraph
for Living Planetary
Systems (ECLIPS)
High
Definition
Imager
(HDI)
LUVOIR
Ultraviolet
Multi-Object
Spectrograph
(LUMOS)
Pollux
Payload
Articulation
System
(PAS)
Bus Sunshade
Mission
Segment
Element
Sub-systems
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 9
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Payload
Element
Spacecraft
Element
Optical
Telescope
Assembly
(OTA)
Extreme
Coronagraph
for Living Planetary
Systems (ECLIPS)
High
Definition
Imager
(HDI)
LUVOIR
Ultraviolet
Multi-Object
Spectrograph
(LUMOS)
Pollux
Payload
Articulation
System
(PAS)
Bus Sunshade
Mission
Segment
Element
Sub-systems
Assemblies
Primary
Mirror
PMSAs PMBSS BSF
Secondary
Mirror
Aft-Optics
System
OTA
Avionics
SMA SMSS
TMA FSM AOSS
MEB PDU LMEB
TMSHarness
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 10
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Payload
Element
Spacecraft
Element
Optical
Telescope
Assembly
(OTA)
Extreme
Coronagraph
for Living Planetary
Systems (ECLIPS)
High
Definition
Imager
(HDI)
LUVOIR
Ultraviolet
Multi-Object
Spectrograph
(LUMOS)
Pollux
Payload
Articulation
System
(PAS)
Bus Sunshade
Mission
Segment
Element
Sub-systems
Assemblies
Primary
Mirror
PMSAs PMBSS BSF
Secondary
Mirror
Aft-Optics
System
OTA
Avionics
SMA SMSS
TMA FSM AOSS
MEB PDU LMEB
VIPPS
2-axis
Gimbal
1-axis
Gimbal
Articulating
ArmTMSHarness
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 11
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Payload
Element
Spacecraft
Element
Optical
Telescope
Assembly
(OTA)
Extreme
Coronagraph
for Living Planetary
Systems (ECLIPS)
High
Definition
Imager
(HDI)
LUVOIR
Ultraviolet
Multi-Object
Spectrograph
(LUMOS)
Pollux
Payload
Articulation
System
(PAS)
Bus Sunshade
Mission
Segment
Element
Sub-systems
Assemblies
Primary
Mirror
PMSAs PMBSS BSF
Secondary
Mirror
Aft-Optics
System
OTA
Avionics
SMA SMSS
TMA FSM AOSS
MEB PDU LMEB
VIPPS
2-axis
Gimbal
1-axis
Gimbal
Articulating
Arm
Structure TMS ACS C&DH Comm.
EPS Propulsion
TMSHarness
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Architecture Diagram
27 November 2018 STDT Face-to-Face Meeting 12
LUVOIR
Ground
Segment
Observatory
Segment
Launch
Segment
Payload
Element
Spacecraft
Element
Optical
Telescope
Assembly
(OTA)
Extreme
Coronagraph
for Living Planetary
Systems (ECLIPS)
High
Definition
Imager
(HDI)
LUVOIR
Ultraviolet
Multi-Object
Spectrograph
(LUMOS)
Pollux
Payload
Articulation
System
(PAS)
Bus Sunshade
Mission
Segment
Element
Sub-systems
Assemblies
Primary
Mirror
PMSAs PMBSS BSF
Secondary
Mirror
Aft-Optics
System
OTA
Avionics
SMA SMSS
TMA FSM AOSS
MEB PDU LMEB
VIPPS
2-axis
Gimbal
1-axis
Gimbal
Articulating
Arm
Structure TMS ACS C&DH Comm.
EPS Propulsion
Deployable
Boom
Systems
Blanket
AssembliesTMSHarness
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LUVOIR-A
27 November 2018 STDT Face-to-Face Meeting 13
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LUVOIR-A Spacecraft Element
27 November 2018 STDT Face-to-Face Meeting 14
Control
Moment
Gyroscopes
(4x)
Sunshade
Deployment
Booms
(4x)
Electrical
Power
System Avionics
Comm.
Star
Trackers
(4x)
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LUVOIR-A Spacecraft Element
27 November 2018 STDT Face-to-Face Meeting 15
Roll-out
Solar
Arrays
(2x)
High-gain
Antenna
System
Separation
Ring
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LUVOIR-A Payload Element
27 November 2018 STDT Face-to-Face Meeting 16
Instrument
Radiators
(270 K, 170 K)
*no longer
deployed*
Instrument
Radiator
(100 K)
HDI
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LUVOIR BSF Design Update
27 November 2018 STDT Face-to-Face Meeting 17
OLD NEW
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LUVOIR-B
27 November 2018 STDT Face-to-Face Meeting 18
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LUVOIR-B Spacecraft Element
27 November 2018 STDT Face-to-Face Meeting 19
Control
Moment
Gyroscopes
(4x)
Sunshade
Deployment
Booms
(4x)
Electrical
Power
System
Avionics
Comm.
Star
Trackers
(4x)
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LUVOIR-B Spacecraft Element
27 November 2018 STDT Face-to-Face Meeting 20
Roll-out
Solar
Arrays
(2x)
High-gain
Antenna
System
Separation
Ring
Thrusters
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LUVOIR-B Payload Element
27 November 2018 STDT Face-to-Face Meeting 21
Instrument
Radiators
(270 K, 170 K)
Instrument
Radiator
(100 K)
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ECLIPS-A/B
• UV Channel:• Imager only
• 3 Apodizers, covering 4-40 λ/D
• Five 10% science bands between 200-525 nm
• VIS Channel:• Imager, R140 IFS
• 4 APLC Apodizers, covering 3.5 –64 λ/D
• 1 VVC Apodizer, covering 2-40 λ/D
• Nine 10% science bands between 515-1030 nm
27 November 2018 STDT Face-to-Face Meeting 22
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ECLIPS-A/B
• NIR Channel:• R70 IFS
• R200 Point-source spectrograph
• No Imager
• 4 APLC Apodizers, covering 3.5-64 λ/D
• 1 VVC Apodizer, covering 2-64 λ/D
• Eight 10% science bands between 1.0-2.0 µm
27 November 2018 STDT Face-to-Face Meeting 23
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HDI-A
• FOV
• UVIS: 3.20 x 1.93’
• NIR: 3.31 x 1.95’
• Resolution:
• UVIS: 3.4 mas/pix
• NIR: 6.9 mas/pix
• Focal Planes:
• UVIS: 1.6 Gpix
• NIR: 0.4 Gpix
• Bandpass:
• UVIS: 200 nm - ~1.0 µm
• NIR: ~800 nm – 2.5 µm
27 November 2018 STDT Face-to-Face Meeting 24
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HDI-B
• FOV
• UVIS: 2.69 x 1.78’
• NIR: 2.71 x 1.79’
• Resolution:
• UVIS: 6.4 mas/pix
• NIR: 12.9 mas/pix
• Focal Planes:
• UVIS: 0.4 Gpix
• NIR: 0.1 Gpix
• Bandpass:
• UVIS: 200 nm - ~1.0 µm
• NIR: ~800 nm – 2.5 µm
27 November 2018 STDT Face-to-Face Meeting 25
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LUMOS-B
• Two Channel Instrument• MOS/Imager
• FUV MOS: 100 – 200 nm
• NUV/VIS MOS: 200 nm – 1.0 µm
• FUV Imager: 100 – 200 nm
• High-resolution Point source spectrograph: 100-200 nm
• FOV:• 2 x 2’ covered by a single MSA tile
of 840 x 480 shutters
27 November 2018 STDT Face-to-Face Meeting 26
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Mass Status – LUVOIR-A
27 November 2018 STDT Face-to-Face Meeting 27
Projected (MEL not
yet finished)
Projected (MEL not
yet finished)
Allocation [kg] Estimate [kg] Difference [kg] Allocation [kg] Estimate [kg] Difference [kg]
Payload OTA Primary Mirror Segment Assemblies (All) 5488.82 7306.08 -1817.26 6098.69 9040.30 -2941.61
Payload OTA PM Backplane Support Structure (PMBSS) 2884.73 2913.53 -28.80 3864.02 3896.02 -32.00
Payload OTA Backplane Support Frame (BSF) 5311.41 3937.22 1374.19 7081.88 5275.58 1806.31
Payload OTA Secondary Mirror Assembly (SMA) 89.71 55.31 34.40 99.68 79.01 20.67
Payload OTA Secondar Mirror Support Stucture (SMSS) 279.09 266.80 12.29 398.70 381.15 17.56
Payload OTA Aft-Optics System (AOS) 348.86 188.45 160.41 498.38 269.21 229.17
Payload OTA Thermal Management System (TMS) 930.30 502.87 427.43 1329.00 718.39 610.61
Payload OTA Payload Power Distribution Unit (PPDU) 29.07 39.60 -10.53 41.53 56.57 -15.04
Payload OTA Payload Main Electronics Box (PMEB) 29.07 30.60 -1.53 41.53 43.71 -2.18
Payload OTA Laser Metrology Electronics Box (LMEB) 0.00 113.18 -113.18 0.00 161.69 -161.69
Payload OTA Harness 93.03 293.89 -200.86 132.90 419.85 -286.95
Payload PAS Vibration Isolation & Precision Pointing System (VIPPS) 186.06 75.08 110.98 265.80 107.26 158.54
Payload PAS Gimbal #1 139.55 46.17 93.38 199.35 65.95 133.40
Payload PAS Gimbal #2 0.00 45.00 -45.00 0.00 64.29 -64.29
Payload PAS Tower / Articulating Arm 232.58 41.01 191.57 332.25 58.58 273.67
Payload HDI High Definition Imager 662.84 663.85 -1.01 946.91 947.93 -1.02
Payload ECLIPS Extreme Coronagraph for Living Planetary Systems 751.22 675.44 75.78 1073.17 964.91 108.26
Payload LUMOS LUVOIR Multi-object Spectrograph 518.64 518.64 0.00 740.92 740.92 0.00
Payload Pollux Pollux 448.87 450.00 -1.13 641.24 642.90 -1.66
Payload Misc Miscellaneous Hardware 69.77 792.74 -722.97 99.68 1132.48 -1032.80
18493.62 18955.44 -461.82 23885.63 25066.68 -1181.05
Spacecraft Bus Structure 2814.16 1101.70 1712.46 4020.23 1573.86 2446.37
Spacecraft Bus Thermal Management System (TMS) 418.64 33.70 384.94 598.05 48.15 549.90
Spacecraft Bus Attitude Control System (ACS) 460.50 251.40 209.10 657.86 359.14 298.72
Spacecraft Bus Propulsion System 162.80 102.70 60.10 232.58 146.71 85.87
Spacecraft Bus Command & Data Handling (C&DH) 46.52 55.60 -9.08 66.45 79.43 -12.98
Spacecraft Bus Communications 69.77 68.54 1.23 99.68 97.91 1.77
Spacecraft Bus Electrical Power System (EPS) 616.32 703.63 -87.31 880.46 1005.19 -124.73
Spacecraft Bus Harness 189.90 88.15 101.75 271.28 125.93 145.35
Spacecraft Sunshade Deployable Boom Assemblies 346.52 384.50 -37.98 495.05 549.28 -54.23
Spacecraft Sunshade Blanket Assemblies 244.90 244.90 0.00 349.86 349.86 0.00
Spacecraft Misc Miscellaneous Hardware 116.29 108.71 7.58 166.13 155.30 10.83
Spacecraft Propellant Propellant 1501.77 2000.00 -498.23 1501.77 2000.00 -498.23
6988.09 5143.53 1844.56 9339.40 6490.76 2848.65
25481.71 24098.96 1382.75 33225.03 31557.43 1667.60
LV Capacity Need: 42076.57
SLS Block 2: 44300.00
LV Margin: 2223.43
Maximum Expected Value (MEV) Mass
Observatory Total:
Payload Totals:
Spacecraft Totals:
Current Best Estimate (CBE) MassAssemblySub-SystemElement
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Mass Status – LUVOIR-B
27 November 2018 STDT Face-to-Face Meeting 28
Projected (MEL not
yet finished)
Projected (MEL not
yet finished)
Allocation [kg] Estimate [kg] Difference [kg] Allocation [kg] Estimate [kg] Difference [kg]
Payload OTA Primary Mirror Segment Assemblies (All) 1518.00 2483.25 -965.25 1897.49 3121.86 -1224.37
Payload OTA PM Backplane Support Structure (PMBSS) 898.44 958.04 -59.60 1203.52 1288.87 -85.35
Payload OTA Backplane Support Frame (BSF) 2257.63 2001.31 256.32 3010.18 2675.02 335.16
Payload OTA Secondary Mirror Assembly (SMA) 31.56 48.24 -16.68 39.45 60.76 -21.31
Payload OTA Secondar Mirror Support Stucture (SMSS) 374.85 340.49 34.36 535.50 486.41 49.09
Payload OTA Aft-Optics System (AOS) 110.25 158.98 -48.73 157.50 227.11 -69.61
Payload OTA Thermal Management System (TMS) 264.60 365.38 -100.78 378.00 521.97 -143.97
Payload OTA Payload Power Distribution Unit (PPDU) 28.88 39.60 -10.72 41.25 56.57 -15.32
Payload OTA Payload Main Electronics Box (PMEB) 28.88 30.60 -1.72 41.25 43.71 -2.46
Payload OTA Laser Metrology Electronics Box (LMEB) 0.00 59.10 -59.10 0.00 84.43 -84.43
Payload OTA Harness 83.94 104.41 -20.47 119.91 149.16 -29.25
Payload PAS Vibration Isolation & Precision Pointing System (VIPPS) 183.75 75.08 108.67 262.50 107.26 155.24
Payload PAS Gimbal #1 139.13 46.17 92.96 198.75 65.95 132.80
Payload PAS Gimbal #2 0.00 45.00 -45.00 0.00 64.29 -64.29
Payload PAS Tower / Articulating Arm 73.50 5.09 68.42 105.00 7.26 97.74
Payload HDI High Definition Imager 455.00 462.17 -7.17 650.00 660.24 -10.24
Payload ECLIPS Extreme Coronagraph for Living Planetary Systems 751.22 751.22 0.00 1073.17 1073.17 0.00
Payload LUMOS LUVOIR Multi-object Spectrograph 518.64 518.64 0.00 740.92 740.92 0.00
Payload Misc Miscellaneous Hardware 52.50 338.04 -285.54 75.00 482.91 -407.91
7770.77 8830.78 -1060.01 10529.39 11917.86 -1388.47
Spacecraft Bus Structure 889.35 889.35 0.00 1270.50 1270.50 0.00
Spacecraft Bus Thermal Management System (TMS) 94.50 33.70 60.80 135.00 48.14 86.86
Spacecraft Bus Attitude Control System (ACS) 103.95 251.40 -147.45 148.50 359.14 -210.64
Spacecraft Bus Propulsion System 51.45 102.70 -51.25 73.50 146.71 -73.21
Spacecraft Bus Command & Data Handling (C&DH) 42.00 55.60 -13.60 60.00 79.43 -19.43
Spacecraft Bus Communications 44.63 68.54 -23.91 63.75 97.91 -34.16
Spacecraft Bus Electrical Power System (EPS) 139.13 703.63 -564.50 198.75 1005.19 -806.44
Spacecraft Bus Harness 58.80 88.15 -29.35 84.00 125.93 -41.93
Spacecraft Sunshade Deployable Boom Assemblies 342.00 384.50 -42.50 488.57 549.28 -60.71
Spacecraft Sunshade Blanket Assemblies 185.00 244.90 -59.90 264.29 349.86 -85.57
Spacecraft Misc Miscellaneous Hardware 52.50 52.50 0.00 75.00 75.00 0.00
Spacecraft Propellant Propellant 540.00 986.10 -446.10 540.00 540.00 0.00
2543.31 3861.07 -1317.76 3401.86 4647.09 -1245.23
10314.08 12691.85 -2377.77 13931.25 16564.95 -2633.70
LV Capacity Need: 22086.60
SLS Block 1B: 37000.00
LV Margin: 14913.40
Current Best Estimate (CBE) Mass Maximum Expected Value (MEV) Mass
Payload Totals:
Spacecraft Totals:
Total:
Element Sub-System Assembly
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Update On Study Deliverables
27 November 2018 STDT Face-to-Face Meeting 29
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Internal Cost Estimates
• All forms submitted to Goddard’s Resource Analysis Office (RAO) on 11/16
• RAO performs parametric cost modeling using high-level cost-estimation relationships (CERs)
• Relate system quantities such as mass, volume, schedule, data rate, pointing accuracy, etc. to cost
• Relatively agnostic to actual hardware implementation
• Forms submitted:
• 2 Mission-level forms (A, B)
• 2 OTA forms (A, B, include Payload Articulation Systems)
• 2 HDI forms (A, B)
• 2 ECLIPS forms (A, B)
• 2 LUMOS forms (A, B)
• 1 Pollux form (A)
• 2 Spacecraft Bus forms (A, B)
• 2 Sunshade forms (A, B)
27 November 2018 STDT Face-to-Face Meeting 30
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Internal Cost Estimates
• Began submitting Master Equipment Lists (MELs) to Goddard’s Cost Estimating, Modeling, and Analysis (CEMA) group
• CEMA also uses parametric cost modeling, but at the lower hardware level
• They’ll use analogous hardware and CERs to cost, for example, each mirror in HDI individually, rather than the instrument as a whole
• Use models and historical data to estimate development, integration, and personnel costs associated with each piece of hardware
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Internal Cost Estimates
• Both groups will provide estimated costs for WBS elements 05 and 06 (Payload and Spacecraft), and wrap factors for elements 01-04 and 07-11 to determine total mission cost
• Both groups will provide a point-design cost for each architecture, as well as an S-curve with confidence-levels indicated
• That is, each group will do a limited cost-risk analysis
• Should have all RAO results, and most (but not all) CEMA results back for CML4 deadline
27 November 2018 STDT Face-to-Face Meeting 32
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System LUVOIR-A LUVOIR-B
OTA (including Payload
Articulation System)
Under Review by
Engineering TeamSubmitted
HDI Submitted Submitted
ECLIPSUnder Review by
Engineering TeamIn Progress
LUMOS Not Started In Progress
Spacecraft (includes Bus
and Sunshade)
Under Review by
Engineering TeamIn Progress
MEL Status
27 November 2018 STDT Face-to-Face Meeting 33
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MEL Example
27 November 2018 STDT Face-to-Face Meeting 34
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Issues
27 November 2018 STDT Face-to-Face Meeting 35
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Vector Vortex Coronagraph
• Recently became aware of a limitation of vector vortex coronagraphs
• Currently baselined as primary coronagraph for LUVOIR-B
• Still gathering information on the topic, so final impact / criticality is not yet known
• Want to give STDT a heads-up
27 November 2018 STDT Face-to-Face Meeting 36
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Vector Vortex Coronagraph
• Issue: Current limitations in liquid crystal mask fabrication require the use of circular polarizers to reduce contrast leakage
• Impact: As currently implemented, a VVC would require a 50% throughput reduction in the coronagraph, reducing exoplanet yields accordingly
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Vector Vortex Coronagraph
• Mitigation: Four options…1. Retain current operational assumption of no
polarizers in beam path with vortex coronagraph• Throughput and yields remain unaffected
• Take a TRL-hit that requires additional development of either liquid crystal masks, or scalar vortex masks
2. Retain current operational assumption of no polarizers in beam path with APLC coronagraph• Throughput and TRL remains unaffected
• Exoplanet yield is reduced
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Vector Vortex Coronagraph
• Mitigation: Four options…(cont.)3. Adopt single polarization operation with a vector
vortex coronagraph• TRL remains the same
• Throughput is reduced by 50%, affecting exoplanet yields
4. Adopt single polarization operation, convert UV channel into a second VIS channel that operates simultaneously in other polarization• Throughput and TRL remains the same
• Exoplanet yields improve slightly
• Loss of UV exoplanet science (200-350 nm)
• Note: this is current HabEx baseline. Drop the “red” channel and convert to second “blue” channel to run two polarizations simultaneously
27 November 2018 STDT Face-to-Face Meeting 39
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Vector Vortex Coronagraph
• Summary:
• *It’s unclear what the actual TRL hit would be. HabEx team claims the existing VVC
technology is TRL 5. LUVOIR has claimed both VVC and APLC are TRL 3.
• HabEx team believes dual polarization liquid crystal masks and scalar vortex
masks are TRL 2.
• Hope to discuss this on Thursday at our joint meeting.
27 November 2018 STDT Face-to-Face Meeting 40
OptionSingle vs. Dual
Polarization
Primary
Coronagraph
Type
Coronagraph
TRL
(currently 3*)
ExoEarth
Candidate
Yield
Coronagraph
Channels
1 Dual
Vortex
(vector or
scalar)
~2 28 UV, VIS, NIR
2 Dual APLC 3* ~16 UV, VIS, NIR
3 Single Vector Vortex 3* 21 UV, VIS, NIR
4 Single Vector Vortex 3* 29 VIS, VIS, NIR
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Questions?
27 November 2018 STDT Face-to-Face Meeting 41